AIRCRAFT LANDING GEAR ACTUATOR

WIPO Patent Application WO/2010/009289

A3

This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions. An actuator (18) is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller (32) in communication with the actuator (18) is configured to command the actuator between the stowed and deployed positions in response to an input. The controller (32) commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator (18) includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.

JP5600155	A drive method of the landing gear of the airplane in the urgent mode
WO/2016/182750	AUTONOMOUS SAFETY AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES
WO/2006/032811	SYSTEM FOR MANEUVERING AN AIRCRAFT LANDING GEAR AND AIRCRAFT COMPRISING SAME

COLLINS ANDREW JOHN (GB)

PCT/US2009/050796

May 20, 2010

July 16, 2009

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HAMILTON SUNDSTRAND CORP (US)
COLLINS ANDREW JOHN (GB)

B64C25/30; B64C25/24; F16H25/20

WO2007099333A1	2007-09-07
WO2007024220A1	2007-03-01

US3904153A	1975-09-09
US4637272A	1987-01-20

GOTTSCHALK, William, S. et al. (Gaskey & Olds P.C.,400 West Maple Road,Suite 35, Birmingham MI, US)

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